US8016229B2 - Retracting air cushioned landing system for air vehicles - Google Patents

Retracting air cushioned landing system for air vehicles Download PDF

Info

Publication number
US8016229B2
US8016229B2 US12/168,393 US16839308A US8016229B2 US 8016229 B2 US8016229 B2 US 8016229B2 US 16839308 A US16839308 A US 16839308A US 8016229 B2 US8016229 B2 US 8016229B2
Authority
US
United States
Prior art keywords
cover
roller
air
air vehicle
bag skirt
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active, expires
Application number
US12/168,393
Other languages
English (en)
Other versions
US20100001128A1 (en
Inventor
Douglas H. Greiner
John P. Morehead
Renee Pasman
Robert R. Boyd
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Lockheed Martin Corp
Original Assignee
Lockheed Martin Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Lockheed Martin Corp filed Critical Lockheed Martin Corp
Priority to US12/168,393 priority Critical patent/US8016229B2/en
Assigned to LOCKHEED MARTIN CORPORATION reassignment LOCKHEED MARTIN CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOYD, ROBERT R., GREINER, DOUGLAS H., MOREHEAD, JOHN P., PASMAN, RENEE
Priority to CA2658321A priority patent/CA2658321C/en
Priority to AU2009201419A priority patent/AU2009201419B2/en
Priority to EP09164336A priority patent/EP2143610B1/en
Publication of US20100001128A1 publication Critical patent/US20100001128A1/en
Priority to US13/158,350 priority patent/US8177161B2/en
Application granted granted Critical
Publication of US8016229B2 publication Critical patent/US8016229B2/en
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60V—AIR-CUSHION VEHICLES
    • B60V3/00—Land vehicles, waterborne vessels, or aircraft, adapted or modified to travel on air cushions
    • B60V3/08—Aircraft, e.g. air-cushion alighting-gear therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/06—Rigid airships; Semi-rigid airships
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/06—Rigid airships; Semi-rigid airships
    • B64B1/24—Arrangement of propulsion plant
    • B64B1/30—Arrangement of propellers
    • B64B1/32—Arrangement of propellers surrounding hull
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B2201/00—Hybrid airships, i.e. airships where lift is generated aerodynamically and statically

Definitions

  • a hybrid air vehicle is a type of air vehicle (may also referred to as an aircraft or an airship) that combines the characteristics of aviation technologies such as heavier-than-air (HTA) aircraft, lighter-than-air (LTA) vehicles, fixed wing aircraft, helicopter, hovercraft and similar others to perform desired functions.
  • Hybrid air vehicles are currently under development that combine the advantages of an aerodynamic shape with the cargo capacity, simplicity, and low operating costs of LTA vehicles. Uses for such vehicles include cargo transport, telecommunications platforms, surveillance, emergency response, advertising platforms, and tourism, among others.
  • LTA vehicles are typically slow and difficult to maneuver. Yet, it is desirable to develop a hybrid air vehicle capable of take off and landing in a minimum amount of space.
  • Traditional LTA vehicles with an air cushioned landing system (ACLS) have been proposed to reduce the take off and landing space requirement.
  • ACLS systems have fixed configurations during take off and landing and also during the flight. This increases drag and reduces fuel efficiency.
  • some LTA vehicles include an ACLS system that is operable in dual modes including a take off and landing mode that is suitable for landing and take off, and a flight mode that is suitable for operation during the flight of the vehicle.
  • traditional tools and techniques that are used for enabling the dual mode ACLS system to transition between the flight mode and the take off and landing mode are often impractical, inefficient, and prone to frequent failures.
  • a hybrid air vehicle in which covers are provided for a plurality of air cushioned landing pads to reduce drag when airborne.
  • Each pad is inflatable to provide an air cushion during touchdown and deflatable during flight of the air vehicle.
  • the cover includes a first cover portion and a second cover portion.
  • a first cover roller of the first cover portion and a matching second cover roller of the second cover portion abut to cover the corresponding pad.
  • the first cover roller and the second cover roller which are separate and free from a physical linkage there between, are separable in an eyelid fashion to expose the corresponding pad.
  • a separation gap between the first cover roller and the second cover roller is increased or decreased by pulling or releasing roller straps to cover or expose the corresponding pad.
  • a cover in other embodiments, includes a first cover portion and a second cover portion.
  • a first cover roller of the first cover portion and a matching second cover roller of the second cover portion abut to cover the corresponding pad.
  • the first cover roller and the second cover roller which are separate and free from a physical linkage there between, are separable in an eyelid fashion to expose the corresponding pad.
  • a separation gap between the first cover roller and the second cover roller is increased by the roller straps to expose the corresponding pad. Evacuating the air from the air cushioned pad enables the cover portions to retract, thereby closing the cover.
  • the ACLS is operable in a combination mode in which the pad is used for distributed support and is also used to provide a vacuum seal between the air vehicle and a ground surface upon touchdown.
  • an air vehicle comprises a bag skirt extendable along a portion of a hull of the air vehicle.
  • the bag skirt is inflatable to provide an air cushion during touchdown and deflatable during flight of the air vehicle.
  • a cover roller is adjacent the first bag skirt.
  • a cover portion is coupled to the cover roller. The cover roller is operable between exposed and unexposed positions to expose and hide the bag skirt with the cover roller.
  • FIG. 1 is a perspective view of an embodiment of a top side of a hybrid air vehicle
  • FIG. 2 is a perspective view of the embodiment of a lower side of a hybrid air vehicle described with reference to FIG. 1 ;
  • FIG. 3 is a front view of an embodiment of a hybrid air vehicle described with reference to FIGS. 1 and 2 ;
  • FIG. 4 is a perspective view of an embodiment of a plurality of air cushioned landing pads shown in a covered position during flight of a hybrid air vehicle described with reference to FIGS. 1 , 2 and 3 ;
  • FIGS. 5A , 5 B, 5 C, 5 D, and 5 E show various views of an air cushioned landing pad (ACLP) in open and closed configuration.
  • ACLP air cushioned landing pad
  • System One or more interdependent elements, components, modules, or devices that co-operate to perform one or more predefined functions.
  • a pressurized air supply may be configured to operate in one of three modes—a blower mode, a suction mode, and a combination mode.
  • a hybrid air vehicle equipped with an air cushioned landing system is described with reference to FIGS. 1 , 2 , 3 and 4 .
  • the hybrid air vehicle equipped with the ACLS offers considerable capability in terms of lifting capacity, operational flexibility, and cost effectiveness.
  • Such an air vehicle has the ability to operate from unimproved landing sites on both land and water.
  • the hybrid air vehicle also has handling characteristics more similar to a hovercraft than a traditional aircraft. Additional detail of an air cushioned landing pad (ACLP) included in the ACLS is described with reference to FIGS. 5A , 5 B, 5 C, and 5 D.
  • ACLP air cushioned landing pad
  • FIG. 1 is a perspective view of an embodiment of the top side of hybrid air vehicle 100 including a plurality of propulsion elements 110 disposed on port, starboard, and aft positions of vehicle 100 .
  • air vehicle 100 has a center gas-filled hull 102 joined longitudinally along a portion of gas-filled side hulls 104 .
  • the use of the side hulls 104 improves the stability of the air vehicle 100 on the ground as well as during flight.
  • the propulsion elements 110 are operable to provide controlled motion in different directions.
  • the aerodynamic shape of hulls 102 , 104 of air vehicle 100 generates lift. Additional lift is provided by a buoyant gas, such as helium, contained in hulls 102 , 104 .
  • the air vehicle 100 may be configured in multiple hull configurations, e.g., with or without the side hulls 104 , with two center hulls, or with one center hull 102 . Similarly, it is understood that the air vehicle 100 may be configured to have less or more number of propulsion elements 110 .
  • the outer surface of air vehicle 100 may be fabricated of a non-rigid sheet material, including composite and/or laminated fabric material. Hulls 102 , 104 are typically pressurized, thereby eliminating the need for internal structure or bracing. Such a design provides a vehicle 100 with resilient external surfaces that is low cost and low weight. The relatively low height to length profile of hulls 102 , 104 provide improved stability and ground handling compared to conventional lighter-than-air vehicles of equal gas volume.
  • FIG. 2 is a perspective view of the lower side of a hybrid air vehicle 100 including the plurality of propulsion elements 110 disposed on port and starboard positions.
  • Gondola 202 is attached to center hull 102 in a longitudinal recess formed by side hulls 104 being positioned slightly lower than center hull 102 .
  • FIG. 3 shows a front view of air vehicle 100 and the vertical position of center hull 102 relative to side hulls 104 .
  • Gondola 202 and/or hulls 102 , 104 can be configured to carry passengers, cargo, on-board computers, cameras and other instruments, GPS, sensors, equipment, and other suitable items/systems.
  • an air cushioned landing system (ACLS) 204 which includes a plurality of air cushioned landing pads 206 , may be configured in accordance with a flight mode of the air vehicle 100 .
  • the ACLS 204 having the plurality of air cushioned landing pads 206 is shown in a deployed (or exposed) position, e.g., during landing, touchdown, and takeoff of the air vehicle 100 .
  • each one of the plurality of air cushioned landing pads 206 includes a plurality of fingers 208 .
  • the plurality of fingers 208 may be separated from one another, thereby allowing them to pass over objects such as tree stumps, rocks, and other terrain.
  • Each one of the plurality of fingers 208 forms an air chamber or air cushion, which may be individually inflated or deflated for improved control. It is understood that a number and shape of the plurality of fingers 208 may vary depending on the application.
  • FIG. 4 is a perspective view of the plurality of air cushioned landing pads 206 shown in a retracted (or covered) position, e.g., during flight of the air vehicle 100 , to reduce drag.
  • a retracted (or covered) position e.g., during flight of the air vehicle 100
  • the profile of the air cushioned landing pads 206 in a covered position is reduced and made more aerodynamic compared to the profile of the pads in a deployed position, thereby reducing drag on the air vehicle 100 . Additional detail of an air cushioned landing pad included in the plurality of air cushioned landing pads 206 is described with reference to FIGS. 5A , 5 B, 5 C, and 5 D.
  • air cushioned landing pads 206 are disposed in a spaced relation, e.g., arranged in an array formation, on the underside of side hulls 104 .
  • the depicted embodiment includes two air cushioned landing pads 206 on the bottom of each side hull 104 . It is understood that depending on the configuration and dimensions of the air vehicle 100 the number and positions of air cushioned landing pads included in the ACLS 204 may be different.
  • ACLS 204 can be positioned fore and aft of the center of gravity of air vehicle 100 to improve the stability and handling of air vehicle 100 during take off, landing, and touchdown.
  • the ACLS 204 enables the air vehicle 100 to be lowered to the ground surface in a controlled manner, e.g., by controlling an amount of the air exhausted from the plurality of air cushioned landing pads 206 , to achieve a soft landing.
  • Gondola 202 may be positioned to enable cargo to be easily off-loaded from a ramp (not shown).
  • the ACLS 204 further enables air vehicle 100 to takeoff and land in relatively small areas and may be used on landing surfaces that are relatively uneven compared to conventional runways. Furthermore, air vehicle 100 may take-off and land on liquid and solid surfaces.
  • the ACLS 204 may be configured to exhaust air from a selective portion of the air cushioned landing pads 206 to create a vacuum seal on the landing surface upon touchdown, thereby providing a stable platform for loading and unloading without the aid of ground crews and tie-down systems.
  • FIG. 5A illustrates a bottom view of an air cushioned landing pad (ACLP) 500 in a deployed (or exposed) configuration, according to some embodiments.
  • FIG. 5B illustrates a cross sectional view (along A-A) of an air cushioned landing pad (ACLP) 500 in a deployed (or exposed) configuration, according to some embodiments.
  • FIG. 5C illustrates a bottom view of an air cushioned landing pad (ACLP) 500 in a retracted (or covered) configuration, according to some embodiments.
  • FIG. 5D illustrates a cross sectional view (along B-B) of an air cushioned landing pad (ACLP) 500 in a retracted (or covered) configuration, according to some embodiments.
  • the ACLP 500 includes a first bag skirt 502 extendable along a portion of the side hull 104 of the air vehicle 100 .
  • first bag skirt 502 is depicted to have an elliptical shape, other shapes including circular are also contemplated.
  • the first bag skirt 502 can be secured to the side hull 104 and is inflatable to provide an air cushion during touchdown. Bag skirt 502 is deflatable during flight of the air vehicle 100 .
  • the ACLP 500 also includes a second bag skirt 504 that is secured to the side hull 104 and is extendable in a volume enclosed by the first bag skirt 502 .
  • First and second bag skirts 502 and 504 may be inflated and deflated separately and individually. It is understood that the use of the second bag skirt 504 can be optional.
  • the first bag skirt 502 and the second bag skirt 504 may include a plurality of fingers 208 ( FIG. 2 ). Fingers 208 may be separated from one another, thereby allowing them to pass over objects such as tree stumps, rocks, and other terrain. Fingers 208 form an air chamber or air cushion, which may be individually or collectively inflated or deflated for improved control. In some embodiments, the first bag skirt 502 and the second bag skirt 504 share a common center. It is understood that the position, size, and the shape of the first bag skirt 502 and the second bag skirt 504 may be different depending on the application.
  • the second bag skirt 504 can be inflated prior to touchdown to provide a first air cushion between the first bag skirt 502 and the second bag skirt 504 and a second air cushion in a volume enclosed by the second bag skirt 504 . Similar to the first bag skirt 502 , the second bag skirt 504 can be deflated to a reduced profile during the flight of the air vehicle 100 . A selective portion of air cushioned landing pads 206 ( FIG. 2 ), e.g., the second bag skirt 504 , can be deflated after touchdown and before takeoff of the air vehicle 100 to provide a vacuum seal between the air vehicle 100 and a landing surface.
  • the ACLP 500 includes cover assemblies 506 that are operable to expose or cover the first bag skirt 502 and the second bag skirt 504 .
  • the cover assemblies 506 may be constructed from any suitable material, for example, nylon fabric, rubber, canvas and reinforced composites.
  • the cover assemblies 506 typically conform substantially to the outer contour of the air vehicle 100 when the first bag skirt 502 and the second bag skirt 504 are covered, thereby reducing the profile and the drag compared to a profile and a drag present when the first bag skirt 502 and the second bag skirt 504 are exposed.
  • cover assemblies 506 include a respective cover portion 508 , 510 ; cover roller 512 , 514 , shaft 522 , anchors 524 , retention straps 526 , and actuators 528 .
  • a first cover roller 512 of the first cover portion 508 and a matching second cover roller 514 of the second cover portion 510 abut to cover the first bag skirt 502 and the second bag skirt 504 .
  • the first cover roller 512 and the second cover roller 514 are separable to expose the first bag skirt 502 and the second bag skirt 504 , thereby generating a separation gap 516 between rollers 512 , 514 .
  • the first cover portion 508 and the second cover portion 510 can include a first edge 518 that is secured to the side hulls 104 , and a second edge 520 that is secured to the periphery of the cover rollers 512 , 514 and is rollable around a corresponding one of the first cover roller 512 and the second cover roller 514 .
  • Rollers 512 , 514 are typically constructed of flexible material that expands lengthwise as rollers 512 , 514 are drawn from closed to open positions. Rollers 512 , 514 can be inflatable to provide additional flexibility.
  • covers 508 , 510 are semi-elliptical and rollers 512 , 514 can be tapered from the central portions toward the end portions to allow covers 508 , 510 to roll smoothly around the periphery of rollers 512 , 514 as rollers 512 , 514 are separated.
  • Covers 508 , 510 and rollers 512 , 514 may have any other suitable shapes in other embodiments.
  • the cover assemblies 506 may be configured to include a single cover portion, e.g., to include one of the respective cover portions 508 or 510 . That is, the cover assemblies 506 may include a single cover portion 508 that can be configured to cover or uncover the first bag skirt 502 (not shown) and/or the second bag skirt 504 (not shown) without generating a separation gap.
  • a shape of the single cover portion 508 may be configured to match a shape of the first bag skirt 502 and the second bag skirt 504 or a desired shape, e.g., elliptical, U-shaped, and similar other.
  • rollers 512 , 514 can be coupled to a respective extensible shaft 522 .
  • shafts 522 are fabricated from elastic material that stretches and retracts as rollers 512 , 514 move between open and closed positions.
  • shafts 522 may be include a spring to provide the desired flexibility in length.
  • shafts 522 run through the center of rollers 512 , 514 forming a core of rollers 512 , 514 , as shown in FIGS. 5B and 5D .
  • Shafts 522 can be capable of being rotated or twisted along a shaft axis and each end of the shafts 522 can be pivotally coupled to the hull 104 by an anchor 524 .
  • shafts 522 may be implemented as a retention strap attached to each end of rollers 512 , 514 that is pivotally secured to anchor 524 .
  • the extensibility of the shafts 520 can provide additional flexibility as rollers 512 , 514 move between open and closed positions.
  • the length of shafts 522 and rollers 512 , 514 vary in accordance with the distance of the separation gap 514 .
  • the length of rollers 512 , 514 and shafts 522 is typically shortest in the covered position ( FIG.
  • the extensibility of shafts 522 also enables the rollers 512 , 514 to abut one another in the covered position.
  • one of the rollers 512 , along with one of the shafts 522 and corresponding anchor 524 may be shifted from the center to an edge, e.g., edge 518 , of the ACLP 500 .
  • the cover assemblies 506 include a first end secured to a hull of the air vehicle and a second end securely wrapped around an extensible shaft to form the cover roller 512 .
  • One roller strap includes a first end secured to a periphery of the cover roller 512 and a second end to operate the cover assemblies 506 .
  • Roller straps 526 corresponding to respective cover portions 508 , 510 are operable to move rollers 512 , 514 between open and closed positions.
  • Roller straps 526 can include a first end secured to a periphery of the respective rollers 512 , 514 and a second end that is coupled to an actuator 528 that is operable to wind and unwind the straps 526 to control the separation gap 516 between rollers 512 , 514 .
  • An actuator 528 such as a motor coupled to operate one or more pulleys or wenches may be used to retract and extend straps 526 .
  • a linear motion of straps 526 causes a rotational motion of the covers 508 , 510 around a portion of a corresponding roller 512 , 514 .
  • the linear motion also causes a rotational motion of a corresponding one of the roller straps 526 around rollers 512 , 514 .
  • the roller straps 526 may be constructed from any suitable material having light weight and high tensile strength such as nylon and/or reinforced composites.
  • the winding of the sheets 508 , 510 is coordinated with the unwinding of the roller straps 526 and vice versa, thereby facilitating a smooth rolling motion of the rollers 512 , 514 .
  • the circumference of rollers 512 , 514 is typically selected so that covers 508 , 510 do not wrap around the entire periphery of rollers 512 , 514 in the open or deployed position, as shown in FIG. 5B , thereby preventing the strap 526 from being trapped under rollers 512 , 514 .
  • strap 526 may be attached to roller 512 , 514 , covers 508 , 510 , and/or extend around rollers 512 , 514 and covers 508 , 510 with one end of strap 526 being fixed and the other end of strap 526 being attached to actuator 528 .
  • the circumference of the rollers 512 , 514 can be selected based on the separation gap 514 required to expose skirts 502 , 504 .
  • one technique to close the cover assembly 506 evacuates the air from the skirts 502 , 504 .
  • the evacuation of air causes the first cover portion 508 and the second cover portion 510 to move toward and abut one another, thereby closing the separation gap 516 .
  • the rollers 512 , 514 remain separate and do not require a physical linkage such as a zipper there between to retract or deploy the ACLP 500 .
  • roller straps 526 may be coupled to a pulley arrangement (not shown) and pulled to increase the separation gap 516 .
  • an increase in the separation gap 516 results in a greater portion of the covers 508 , 510 being rolled around the cover rollers 512 , 514 compared to the separation gap 516 being substantially equal to zero.
  • the separation gap 516 can have a non-linear shape, which varies from being closed to having a maximum value where the non-linear shape substantially matches a shape of the first bag skirt 502 , thereby exposing it.
  • the roller straps 526 may be released when the air evacuation system is enabled to operate the ACLP 500 is a covered mode (the separation gap 516 having a zero value) and the roller straps 526 may be retracted to separate the first cover roller 512 and the second cover roller 514 (the separation gap 516 having a maximum value), thereby exposing skirts 502 , 504 .
  • the roller straps 526 may be pulled to an open position (not shown) to expose the first bag skirt 502 in preparation for landing and prior to the touchdown and released to a closed position to cover the bag skirts 502 , 504 after takeoff and during the flight.
  • a pressurized air source 530 can be included in ACLP 500 to provide air to inflate bag skirts 502 , 504 , including any air cushions formed there between and including the plurality of the fingers 208 ( FIG. 2 ).
  • the air pressurized source 530 is operable in one of multiple modes in accordance with a flight status of the air vehicle 100 .
  • the multiple modes include a suction (or vacuum) mode to deflate the bag skirts 502 , 504 , a blower mode to inflate (or pressurize) the bag skirts 502 , 504 , and a combination mode to selectively inflate the first bag skirt 502 and deflate a second bag skirt 504 (or deflate the first bag skirt 502 and inflate a second bag skirt 504 ).
  • the blower mode increases the separation gap 516 to expose the skirts 502 , 504 .
  • the suction mode causes the bag skirts 502 , 504 to be covered by the cover assemblies 506 and have a reduced profile compared to the profile in the blower mode, thereby reducing drag on the air vehicle 100 during the flight.
  • the combination mode which may be selected after the touchdown and before the takeoff of the air vehicle, enables the ACLP 500 to provide distributed support and also enables the ACLP 500 to provide a vacuum seal between the air vehicle 100 and a ground surface.
  • the embodiments disclosed provide an ACLS for an air vehicle having an improved cover for the air cushioned landing pad to reduce drag during flight.
  • the tools and techniques described herein provide a simple, reliable, non-interlocking type cover that is suitable for use in an aerospace environment.
  • the cover includes a first cover portion and a second cover portion.
  • a first cover roller of the first cover portion and a matching second cover roller of the second cover portion abut to cover the corresponding pad.
  • the first cover roller and the second cover roller which are separate and free from a physical linkage there between, are separable in an eyelid fashion to expose the corresponding pad.
  • a separation gap between the first cover roller and the second cover roller is increased or decreased by at least one strap to cover or expose the corresponding pad.
  • the ACLS is operable in a combination mode in which the pad is used for distributed support and is also used to provide a vacuum seal between the air vehicle and a ground surface upon touchdown.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Transportation (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Tents Or Canopies (AREA)
  • Motorcycle And Bicycle Frame (AREA)
  • Seats For Vehicles (AREA)
US12/168,393 2008-07-07 2008-07-07 Retracting air cushioned landing system for air vehicles Active 2030-02-15 US8016229B2 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US12/168,393 US8016229B2 (en) 2008-07-07 2008-07-07 Retracting air cushioned landing system for air vehicles
CA2658321A CA2658321C (en) 2008-07-07 2009-03-13 Retracting air cushioned landing system for air vehicles
AU2009201419A AU2009201419B2 (en) 2008-07-07 2009-04-08 Retracting air cushioned landing system for air vehicles
EP09164336A EP2143610B1 (en) 2008-07-07 2009-07-01 Retracting Air Cushioned Landing System for Air Vehicles
US13/158,350 US8177161B2 (en) 2008-07-07 2011-06-10 Retracting air cushioned landing system for air vehicles

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/168,393 US8016229B2 (en) 2008-07-07 2008-07-07 Retracting air cushioned landing system for air vehicles

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US13/158,350 Division US8177161B2 (en) 2008-07-07 2011-06-10 Retracting air cushioned landing system for air vehicles

Publications (2)

Publication Number Publication Date
US20100001128A1 US20100001128A1 (en) 2010-01-07
US8016229B2 true US8016229B2 (en) 2011-09-13

Family

ID=41137211

Family Applications (2)

Application Number Title Priority Date Filing Date
US12/168,393 Active 2030-02-15 US8016229B2 (en) 2008-07-07 2008-07-07 Retracting air cushioned landing system for air vehicles
US13/158,350 Active US8177161B2 (en) 2008-07-07 2011-06-10 Retracting air cushioned landing system for air vehicles

Family Applications After (1)

Application Number Title Priority Date Filing Date
US13/158,350 Active US8177161B2 (en) 2008-07-07 2011-06-10 Retracting air cushioned landing system for air vehicles

Country Status (4)

Country Link
US (2) US8016229B2 (pt)
EP (1) EP2143610B1 (pt)
AU (1) AU2009201419B2 (pt)
CA (1) CA2658321C (pt)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100230533A1 (en) * 2009-03-13 2010-09-16 Greiner Douglas H System and Methods for Buoyancy Management in an Airship
US20120037748A1 (en) * 2010-08-10 2012-02-16 IREL Solutions Group Ltd. Airship
US8783602B2 (en) 2012-04-17 2014-07-22 Lockheed Martin Corporation System and method for furling an air cushion landing system
US20150078620A1 (en) * 2012-04-20 2015-03-19 Eth Zurich Aircraft, Methods for Providing Optical Information, Method for Transmission of Acoustic Information and Method for Observing or Tracking an Object
US20150203184A1 (en) * 2014-01-17 2015-07-23 Joseph Nilo Sarmiento Sail-equipped amphibious aerostat or dirigible
US20220315196A1 (en) * 2019-07-16 2022-10-06 Hybrid Air Vehicles Limited Landing apparatus for an air vehicle
US11745844B2 (en) 2019-05-10 2023-09-05 Hybrid Air Vehicles Limited Aircraft and systems therefor

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8894002B2 (en) 2010-07-20 2014-11-25 Lta Corporation System and method for solar-powered airship
US8042772B2 (en) 2008-03-05 2011-10-25 The Boeing Company System and method for pneumatically actuating a control surface of an airfoil
US8931739B1 (en) * 2009-12-08 2015-01-13 The Boeing Company Aircraft having inflatable fuselage
US8727280B1 (en) 2009-12-08 2014-05-20 The Boeing Company Inflatable airfoil system having reduced radar and infrared observability
USD670638S1 (en) * 2010-07-20 2012-11-13 Lta Corporation Airship
AU2012236872B2 (en) 2011-03-31 2017-02-02 Lta Corporation Airship including aerodynamic, floatation, and deployable structures
US9845141B2 (en) * 2012-12-07 2017-12-19 Raven Industries, Inc. Atmospheric balloon system
CN103407444B (zh) * 2013-08-05 2016-05-25 北京理工大学 基于垫升起降技术的固定翼飞行器
US9428257B2 (en) * 2013-09-18 2016-08-30 William Edmund Nelson Extended endurance air vehicle
GB2518428A (en) * 2013-09-23 2015-03-25 Hybrid Air Vehicles Ltd Landing Systems for air vehicles
USD743319S1 (en) * 2014-05-05 2015-11-17 Lta Corporation Airship
USD743867S1 (en) * 2014-05-05 2015-11-24 Lta Corporation Airship
CN104118555B (zh) * 2014-07-14 2016-08-24 北京大学 一种无人自主飞艇及其飞行控制系统的建立方法
US20160221661A1 (en) 2015-02-02 2016-08-04 Derek Lee Bohannon Tendon sleeve for high-altitude balloon and system for making the same
CN104986319B (zh) * 2015-07-21 2017-06-16 中国科学院光电研究院 一种矢量推进装置、飞艇以及矢量推进装置的安装方法
JP1550911S (pt) * 2015-10-30 2016-06-06
CN105947170B (zh) * 2016-05-31 2018-12-18 中国科学院光电研究院 一种系留气球的可拆卸防风罩及系留气球
CN106240785B (zh) * 2016-08-24 2018-04-24 达天飞艇（宁夏）有限公司 辅升气球带宽体可变翼的平流层飞艇稳态升降的方法
CN106564580B (zh) * 2016-10-19 2019-02-19 南京达索航空科技有限公司 一种飞艇
CN106741813A (zh) * 2017-01-17 2017-05-31 南京柯尔航空科技有限公司 一种扑翼飞艇
CN109720534A (zh) * 2019-02-28 2019-05-07 北京空天高科技有限公司 一种平流层飞艇
CN109693778A (zh) * 2019-02-28 2019-04-30 北京空天高科技有限公司 一种平流层飞艇
CN110015396B (zh) * 2019-04-08 2022-05-27 上海交通大学 一种大尺度半刚性结构飞艇
IT202000015880A1 (it) * 2020-07-01 2022-01-01 C I R A Centro Italiano Ricerche Aerospaziali S C P A Dirigibile stratosferico ibrido tattico

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1457774A (fr) 1965-10-13 1966-01-24 Westland Aircraft Ltd Perfectionnements apportés aux véhicules à coussin d'air
US3869103A (en) 1973-10-12 1975-03-04 Us Navy Retraction system for double pod air cushion landing gear system
US4019698A (en) * 1976-03-25 1977-04-26 Textron, Inc. Air cushion undercarriage brake system
US4131175A (en) * 1975-06-20 1978-12-26 British Hovercraft Corporation Ltd. Air cushion vehicles
US5909857A (en) * 1995-10-31 1999-06-08 Filimonov; Alexandr Iosifovich Filimonov hybrid dirigible craft
WO2003047967A1 (en) 2001-12-05 2003-06-12 Advanced Technologies Group Limited Lighter-than-air aircraft with air cushion landing gear means

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2074112A (en) * 1980-04-19 1981-10-28 Phoenix Hovercraft Corp Improvements in or relating to gas-cushion vehicles

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1457774A (fr) 1965-10-13 1966-01-24 Westland Aircraft Ltd Perfectionnements apportés aux véhicules à coussin d'air
US3869103A (en) 1973-10-12 1975-03-04 Us Navy Retraction system for double pod air cushion landing gear system
US4131175A (en) * 1975-06-20 1978-12-26 British Hovercraft Corporation Ltd. Air cushion vehicles
US4019698A (en) * 1976-03-25 1977-04-26 Textron, Inc. Air cushion undercarriage brake system
US5909857A (en) * 1995-10-31 1999-06-08 Filimonov; Alexandr Iosifovich Filimonov hybrid dirigible craft
WO2003047967A1 (en) 2001-12-05 2003-06-12 Advanced Technologies Group Limited Lighter-than-air aircraft with air cushion landing gear means
US7040572B2 (en) * 2001-12-05 2006-05-09 Advanced Technologies Group Limited Lighter-than-air aircraft with air cushion landing gear means

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100230533A1 (en) * 2009-03-13 2010-09-16 Greiner Douglas H System and Methods for Buoyancy Management in an Airship
US8167240B2 (en) * 2009-03-13 2012-05-01 Lockheed Martin Corporation System and methods for buoyancy management in an airship
US20120037748A1 (en) * 2010-08-10 2012-02-16 IREL Solutions Group Ltd. Airship
US8973865B2 (en) * 2010-08-10 2015-03-10 IREL Solutions Group Ltd. Tri-hull dirigible airship
US8783602B2 (en) 2012-04-17 2014-07-22 Lockheed Martin Corporation System and method for furling an air cushion landing system
US20150078620A1 (en) * 2012-04-20 2015-03-19 Eth Zurich Aircraft, Methods for Providing Optical Information, Method for Transmission of Acoustic Information and Method for Observing or Tracking an Object
US20150203184A1 (en) * 2014-01-17 2015-07-23 Joseph Nilo Sarmiento Sail-equipped amphibious aerostat or dirigible
US11745844B2 (en) 2019-05-10 2023-09-05 Hybrid Air Vehicles Limited Aircraft and systems therefor
US20220315196A1 (en) * 2019-07-16 2022-10-06 Hybrid Air Vehicles Limited Landing apparatus for an air vehicle
US11884376B2 (en) * 2019-07-16 2024-01-30 Hybrid Air Vehicles Limited Landing apparatus for an air vehicle

Also Published As

Publication number Publication date
EP2143610B1 (en) 2012-09-05
EP2143610A2 (en) 2010-01-13
EP2143610A3 (en) 2011-06-22
US20100001128A1 (en) 2010-01-07
CA2658321A1 (en) 2010-01-07
AU2009201419B2 (en) 2013-01-10
US20120043416A1 (en) 2012-02-23
US8177161B2 (en) 2012-05-15
CA2658321C (en) 2016-06-21
AU2009201419A1 (en) 2010-01-21

Similar Documents

Publication Publication Date Title
US8016229B2 (en) Retracting air cushioned landing system for air vehicles
US7040572B2 (en) Lighter-than-air aircraft with air cushion landing gear means
US7487936B2 (en) Buoyancy control system for an airship
US6648272B1 (en) Airship
US5005783A (en) Variable geometry airship
US11305863B1 (en) Hybrid lighter-than-air vehicle
RU2264315C2 (ru) Гибридный летательный аппарат
US2886265A (en) Light weight pneumatic airplane
US6824098B1 (en) VTOL parafoil aircraft
WO2007024965A2 (en) Aerodynamic fairing system for airship
GB2445744A (en) Air-cushion landing system for a hybrid air vehicle which is mounted on the underside of the payload module or passenger cabin
US8864068B1 (en) Multi-chamber landing system for an air vehicle
US9592906B2 (en) Air cushioned landing system for air vehicles
CA2557771A1 (en) Hybrid airship
US11884376B2 (en) Landing apparatus for an air vehicle
CN106394853A (zh) 一种飞艇
CA2545442A1 (en) Morphing hybrid airship

Legal Events

Date Code Title Description
AS Assignment

Owner name: LOCKHEED MARTIN CORPORATION, MARYLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MOREHEAD, JOHN P.;GREINER, DOUGLAS H.;PASMAN, RENEE;AND OTHERS;REEL/FRAME:021199/0897

Effective date: 20080522

STCF Information on status: patent grant

Free format text: PATENTED CASE

FPAY Fee payment

Year of fee payment: 4

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 8TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1552); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 8

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 12TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1553); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 12